EP1197315A2 - Procédé pour la fabrication des préformes en matière composite renforcées par des fibres et préforme ainsi obtenue - Google Patents

Procédé pour la fabrication des préformes en matière composite renforcées par des fibres et préforme ainsi obtenue Download PDF

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Publication number
EP1197315A2
EP1197315A2 EP01124219A EP01124219A EP1197315A2 EP 1197315 A2 EP1197315 A2 EP 1197315A2 EP 01124219 A EP01124219 A EP 01124219A EP 01124219 A EP01124219 A EP 01124219A EP 1197315 A2 EP1197315 A2 EP 1197315A2
Authority
EP
European Patent Office
Prior art keywords
semi
resin
layers
finished
fiber composite
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP01124219A
Other languages
German (de)
English (en)
Other versions
EP1197315A3 (fr
Inventor
Torsten Lorenz
Franz Stadler
Stefan Utecht
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Defence and Space GmbH
Original Assignee
EADS Deutschland GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by EADS Deutschland GmbH filed Critical EADS Deutschland GmbH
Publication of EP1197315A2 publication Critical patent/EP1197315A2/fr
Publication of EP1197315A3 publication Critical patent/EP1197315A3/fr
Withdrawn legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/40—Shaping or impregnating by compression not applied
    • B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29B—PREPARATION OR PRETREATMENT OF THE MATERIAL TO BE SHAPED; MAKING GRANULES OR PREFORMS; RECOVERY OF PLASTICS OR OTHER CONSTITUENTS OF WASTE MATERIAL CONTAINING PLASTICS
    • B29B15/00—Pretreatment of the material to be shaped, not covered by groups B29B7/00 - B29B13/00
    • B29B15/08—Pretreatment of the material to be shaped, not covered by groups B29B7/00 - B29B13/00 of reinforcements or fillers
    • B29B15/10—Coating or impregnating independently of the moulding or shaping step
    • B29B15/105—Coating or impregnating independently of the moulding or shaping step of reinforcement of definite length with a matrix in solid form, e.g. powder, fibre or sheet form
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/40—Shaping or impregnating by compression not applied
    • B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
    • B29C70/46—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
    • B29C70/465—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating by melting a solid material, e.g. sheets, powders of fibres
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
    • B29C70/543—Fixing the position or configuration of fibrous reinforcements before or during moulding
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
    • Y10T428/24752—Laterally noncoextensive components
    • Y10T428/2476—Fabric, cloth or textile component

Definitions

  • the invention relates to a method for producing preforms Fiber composite semi-finished products, as well as one manufactured by such a method Preform.
  • fiber composite materials are made of CFRP (carbon fiber reinforced Plastic), GRP (glass fiber reinforced plastic), AFK (aramid fiber reinforced Plastics), BFK (boron fiber reinforced plastics). Hybrid materials (i.e. a mixture of these materials) can also be used such as. CFRP fabric with woven AFK rovings etc. used become.
  • the fiber components, hereinafter called fibers are the semi-finished fiber composite made of carbon fibers, glass fibers, aramid and / or Boron fibers formed. You can use it, for example, as a woven fabric, as a multi-axial scrim or be designed as chain-reinforced unidirectional semi-finished products.
  • suitable Resins are, for example, all epoxy prepreg resins.
  • the general state of the art semi-finished textile as starting materials used by at least one scrim, fabric or knitted fabric, so generally a textile fabric can be formed.
  • the textile semi-finished products are placed in a device which is a negative form of the to be manufactured Component represents, which are already provided with resin or in the device be provided with resin. After a curing process it can cured material can be removed as a component of the device.
  • a disadvantage of this method is that the individual layers are individually coated with resin must be soaked and the workers with liquid health hazardous Working materials (resin) have to handle. Also the one to be introduced liquid amount of resin depending on the application method, for example By hand with a brush or by means of a watering device, from component to component and method of working, vary widely so that a consistent quality of each achieved result can not be guaranteed.
  • Preforms from several pieces and / or sections of semi-finished fiber composite products be formed before the fiber composite semi-finished product resin is added.
  • Preforms are precursors of what is to be manufactured Component that already have the design of the latter. These can be for Components with developable, non-developable and not fully developable Geometry are formed. As unwindable or not unwindable the property of the component is referred to as such on a roll to be wound and unwound or not.
  • Various processes are known for such preforms:
  • binder technology dry fiber composite semi-finished products are made with binders, i.e. with binders usually in powder form, moved and then merged as packages. In this composition they are fixed, for example, by appropriate heating. Complex components are made by hand or with the help of rubber membranes shaped.
  • the binder technology has the disadvantage that the semi-finished fiber composite must be specially prepared and that provided with the binders Material - comparable to prepregs - must be stored refrigerated.
  • the binders must be specially manufactured and qualified. You must not cause unwanted side reactions with those used later Resins. This is problematic because not every common one Resin system a suitable binder variant is available. In these cases are losses in their mechanical properties in systems with binders to accept the same fiber material without binder.
  • the dry semi-finished fiber composite can be sewn together in a desired composition.
  • sewing techniques including tufting, crochet or Knitting, used.
  • This method has the disadvantage that in particular elaborate auxiliary tools are required for spatial sewing, their complexity a frequent change of the clamping or the respective Require device and thus increase the susceptibility to errors. moreover are the preparations for sewing processes and the sewing processes themselves and time-consuming and therefore also cost-intensive.
  • the invention has for its object an improved process for the production of Preforms made of semi-finished fiber composites and one produced by them To provide preform.
  • the invention has the advantage over the prior art that neither a special preparation of the fiber composite semi-finished products with binders Sewing process with the resulting effort is required.
  • Another advantage of the subject matter of the invention is that the raw materials resin film and fiber material only come together when the preform is being produced, and the costly cooling storage is thus eliminated.
  • the amount of resin introduced is clearly reproducible due to the number of layers of the resin film with the corresponding basis weight in g / m 2 . It is also possible to use the invention in resin systems which are not suitable for binder technology, for example when epoxy resin systems are used as a semi-finished resin film.
  • the method according to the invention turns a scrim from at least two Layers of a dry semi-finished fiber composite and at least one layer Resin is made that is initially separated from each other in a way be layered that from the resulting scrim in one Draping process of preform 1 of predetermined shape are formed can.
  • the preform can generally also be a preform, i.e. on Intermediate product for the production of a preform.
  • alternating layers of prefabricated, dry Fiber composite semifinished product and resin layers placed one on top of the other Resin layers connect the facing sides of the semi-finished blanks guaranteed in their coverage areas, insofar as they do not represent the outside of the later preform.
  • the resin layers thus have a shape that connects inner semi-finished blanks and the mutually facing sides from the outside of the preform-forming semi-finished blanks in their overlapping areas guarantee.
  • the resin layers have local recesses have to form the individual profile parts (A, B, C, D) of the scrim in the area of the local recesses shear stresses between the 3 is, for example, such a fabric shown, which has the scrim layers 3a, 3b, 3c, 3d, 3e, 3f.
  • the preform is generally made up of several parts, the general each have a different number of semi-finished layers or resin layers have, which result from the respective shape of the dry semi-finished blanks and the resin layers. These parts can be angled to each other be arranged. Also protruding areas can be of individual Scrim layers are angled out from another area to form the former stiffening segments, foot layers, flanges or the like. It is usually necessary for the outside of the individual Areas from the corresponding areas of the semi-finished product blanks be formed, i.e. that the resin layers in the areas between outer Semi-finished product layers are located.
  • the scrim which consists of the semi-finished layers and the Resin films is formed to form the preform of predetermined shape
  • the resin layers used to connect the facing sides the semi-finished blanks are provided in their overlap areas, there local recesses to bend or move the corresponding Allow parts A, B, C, D of the clutch.
  • those required to form such a scrim 3 are used Semi-finished blanks 10 of dry, i.e. no resin or glue fiber composite semi-finished products according to a corresponding design specification individually cut.
  • the individual semi-finished products can be cut 10 cut from a rolled semi-finished roll 20 be (Fig. 1).
  • the cut is made, for example, on a flat surface or on a cutter table.
  • the semi-finished blanks 10 can initially marked and then cut out with a knife by hand or machine become.
  • the scrim 3 between the semifinished layers Resin is placed in the form of a resin film on or between layers the layers of semi-finished blanks inserted between them.
  • the clutch 3 can be opened a corresponding curing tool 70, the appropriate one Edges or contact surfaces to support the draping process.
  • the Technology achieved a curing of the preform 1. From the preform 1 the component to be manufactured can then be formed.
  • the resin film 30 can also be applied before cutting the dry semi-finished product the intended coverage area of the semi-finished product (10) is applied the cutting of the semi-finished product (10) he follows.
  • dry semi-finished blanks are used alternately with the resin layers.
  • the resin layers are preferably made from resin films, i.e. from resin film blanks the same formed.
  • the resin is intended for the individual To connect layers of semi-finished products. It may be provided that to provide local recesses in the resin film for forming. This allows the forming properties of the scrim or the Control the preform to be manufactured, since the dry semi-finished fiber composite in these areas with predetermined by the material Can shift frictional thrust resistances against each other.
  • Design specification for the formation of the semi-finished blanks and if necessary the resin film blank is defined so that at a predetermined Arrangement of the blanks or the lay-up layers to form the one to be produced Preform 1 is possible and in subsequent process steps is achieved.
  • the working surface 60 preferably has a separating film 61 that can serve as a carrier for the preform.
  • the work surface 60 has expediently a reference system or a reference device, which, for example, by a stop 61 or by a sheet or by Laser pointer points (the latter two not shown) is realized.
  • the work surface 60 can in turn be covered with a resin layer or a layer Resin film be prepared to the scrim 3 or the preform 1 during their Fix machining.
  • a first dry semi-finished blank 11 is thus placed on the work surface 60 hung up.
  • a resin layer e.g. be attached in the form of a resin film blank 31.
  • the first procedure has the advantage that the backing paper or the carrier film 50 of the resin film blank 30 generally very sensitive dry semi-finished blank 10 when applied to the work surface 60 stabilized. This aspect is of course every time one is applied Resin film blank 30 relevant.
  • a resin film blank 30 For applying a resin film blank 30 to the respective semi-finished blank 10 become corresponding resin film blanks 30 made of a resin film 40 cut out (Fig. 2), at least on one side on a backing paper or a carrier film 50 is applied, and the individual resin film blanks 30 each positioned on at least one semi-finished blank 10.
  • the resin film blanks 30 can shape and size of the semi-finished blanks 10 fully correspond. But it is also possible that they are have a different shape to only partial areas of the semi-finished blanks 10 to connect with each other.
  • a pressure roller can be used for pressing or a vacuum membrane (both not shown) is used become.
  • a first scrim layer 3a with a first with its underside on the Working surface 60 positioned semi-finished blank 11, on the top a first resin film blank 31 is attached. It can also at the Another resin layer 30 on the underside of the first semi-finished blank 11 be provided.
  • the first resin film blank 31 can also be a backing paper or have a carrier film 51 on its upper side.
  • the after this Process step resulting layer sequence seen from the work surface 60 So is: work surface 60, optionally a release film 61 for fixing the resulting scrim 3, a first semi-finished blank 11, a first resin film blank 31 and a first carrier paper or a carrier film 51.
  • the carrier paper or the carrier film 51 are removed and a second semi-finished blank 12 is applied.
  • This can, like already the first semi-finished blank 11 already with a second or another Resin film blank 32 may or may not be provided.
  • additionally can also be another or third resin film blank 32b on the bottom this semifinished blank 12 can be attached (this constellation is in the Figure 3 not shown).
  • the range between the first 11th and the second 12 semi-finished blank two layers of resin film blanks 32, 32b arranged. It is also possible in principle, all layers of semi-finished blanks 10, 11, 12 only on the underside with one Resin film blank 30 to be provided.
  • a fabric 3 is made with a predetermined fabric thickness at least one scrim layer 3a, 3b, 3c, 3d, 3e, 3f is formed. Every layer of scrim has a semi-finished blank 10 and at least one resin film blank 30 on either the top, i.e. regarding each Semi-finished product cut on the side beyond the work surface 60, or is arranged on the underside or on both sides.
  • Prefabricated dry fiber composite fabrics are then placed on a suitable one Hardening tool 70 transferred and in stages in all necessary Layers reshaped or draped ( Figures 4 and 5a-c).
  • the shape of the scrim 3 and the type of draping and reshaping of the same on the Hardening tool 70 is provided in such a way that the shape of the material to be produced is thereby achieved Preform can be formed from the clutch 3. this will described below using a few examples:
  • the scrim layer 4a has a semi-finished blank 21 and one arranged above it Resin film blank 41, the scrim layer 4b, a semi-finished blank 22 and a resin film blank 42 arranged above it, the scrim layer 4c one Semi-finished product blank 23, the lay-up layer 4d a resin film blank 44 and a semifinished blank 24 arranged above it, the scrim layer 4e a resin film blank 45 and a semi-finished blank arranged above it 25 on.
  • the scrim 3 or the preform P according to FIGS. 5a-5c is as follows built: on the work surface 60 or the curing tool 70 is first a first semi-finished blank 21 stored, which in its flat Extension of the area of an inner overlap region 38b of the scrim 4 corresponds.
  • Parts of individual scrim layers 4b, 4d thus protrude, namely areas of the Semi-finished blanks 22 and 24 and the resin film blanks 42 and 44 an inner overlap area 38b out from the longitudinal extent a plurality of scrim layers 4a, 4c, 4e is determined. Out this can be followed by a connecting part D and a stiffening part or frame C and foot layers A, B are formed.
  • the inner coverage area 38b, from which a connecting part D is subsequently formed, is formed by determined a scrim area, which in the manufacture of the preform as Whole should be treated. That its locations are shown in subsequent Steps for producing the preform 1 are not separated. In this Area 38b forms the semifinished layers 22, 23, 24 inner layers.
  • the protruding areas of the resin film blanks 42 and 44 are between the protruding areas of the semi-finished blanks 22 and 24 are arranged, so that according to their respective neighborhood for mutual investment can be brought (Fig. 5b), although in the initial situation do not have to represent immediately adjacent layers. Doing so again those sides laid together and with each other by means of resin layers connected, no outsides in the preform to be produced form.
  • the second 22 and fourth 24 semi-finished products can therefore be cut using the second and third resin film blanks 42 and 44 in a partial area with one another connected, although both of them in the stack only with the third Semi-finished product cut 23 are immediately adjacent.
  • the stand out Ends of the resin film blanks 42, 44 shorter than the protruding ones Ends of the semi-finished blanks 22, 24 so that the overlap area 38b protruding ends of the semi-finished blanks 22 and 24, as shown in Fig. 5c, can be further individually deformed. That's the way it is For example, possible from a flat scrim 4 a preform with a To form a profile with foot layers A and B protruding from both sides, in which case the connection to a subsequent or substructure (not shown) possible is.
  • the preform 1 is also additional resin impregnated and cured. Doing so will cure injected or otherwise applied to the preform.
  • resin of the prior art is considered, e.g. Epoxy, polyester, Polyimide or polyamide resins. Any method can be used State of the art can be applied. In particular, this can be necessary Resin according to the so-called Resin Film Infusion (RFI) process in the form of the above resin films.
  • RTM resin transfer molding
  • RI resin infusion process
  • the applicability of each method depends on the compatibility of the various resin systems used. If this is given So two or more different resin systems can be used each epoxy resin system becoming liquid at a certain temperature. When resin systems are used, the chemical is essentially the same Have composition, these can also be mixed, so that different resins can be used in one component.
  • the resin used for the impregnation can be mixed with the resin, which is used for the creation of the preform P must be identical. It However, it is generally sufficient if both resins are chemically compatible, i.e. if they have a chemical suitable for the production of the fiber composite component Respond.
  • the preform to be produced can be completely or partially unwound Have geometry.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Textile Engineering (AREA)
  • Moulding By Coating Moulds (AREA)
  • Reinforced Plastic Materials (AREA)
EP01124219A 2000-10-13 2001-10-15 Procédé pour la fabrication des préformes en matière composite renforcées par des fibres et préforme ainsi obtenue Withdrawn EP1197315A3 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10050851A DE10050851A1 (de) 2000-10-13 2000-10-13 Verfahren zur Herstellung von Vorformlingen aus Faser-Verbund-Materialien, sowie ein daraus hergestellter Vorformling
DE10050851 2000-10-13

Publications (2)

Publication Number Publication Date
EP1197315A2 true EP1197315A2 (fr) 2002-04-17
EP1197315A3 EP1197315A3 (fr) 2004-01-28

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP01124219A Withdrawn EP1197315A3 (fr) 2000-10-13 2001-10-15 Procédé pour la fabrication des préformes en matière composite renforcées par des fibres et préforme ainsi obtenue

Country Status (4)

Country Link
US (2) US20020053400A1 (fr)
EP (1) EP1197315A3 (fr)
CA (1) CA2358945A1 (fr)
DE (1) DE10050851A1 (fr)

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EP1900502A1 (fr) * 2006-09-13 2008-03-19 General Electric Company Procédé de fabrication d'un coin composite
EP2266784A1 (fr) 2009-06-22 2010-12-29 Eurocopter Deutschland GmbH Procédé pour la fabrication d'un composant de sandwich doté d'un cýur en nid d'abeille
EP2384884A1 (fr) * 2010-05-07 2011-11-09 Eurocopter Deutschland GmbH Procédé de fabrication d'une pièce composite renforcée et pièce composite renforcée obtenue selon ledit procédé
EP2311618A3 (fr) * 2002-07-18 2013-08-14 Mitsubishi Rayon Co., Ltd. Préimprégné et méthode de fabrication d'un préimprégné
EP3034283A1 (fr) * 2014-12-18 2016-06-22 Airbus Operations Limited Procédé de fabrication d'une structure composite laminaire
EP3210768A3 (fr) * 2016-02-05 2017-11-22 Rohr, Inc. Procédé de fabrication de structures composites au moyen d'un film de résine combiné et d'un tissu sec
CN109269855A (zh) * 2018-10-22 2019-01-25 西安航空制动科技有限公司 一种c纤维预制体力学性能试样的制备方法

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GB0205498D0 (en) * 2002-03-08 2002-04-24 Structural Polymer Systems Ltd Moulding material
DK1603723T4 (en) 2003-03-06 2018-10-15 Vestas Wind Sys As Preform and method of preparing a preform
DE10332969A1 (de) * 2003-07-21 2005-02-10 Ise Innomotive Systems Europe Gmbh Modulträger-Teil und Verfahren zu seiner Pressformung
CN1938137B (zh) * 2004-03-30 2013-07-03 东丽株式会社 预成型体、frp及其制造方法
DE102006031491B4 (de) 2005-07-19 2010-09-30 Eurocopter Deutschland Gmbh Verfahren zur Herstellung eines dreidimensional gekrümmten Faserverbundwerkstoff-Strukturbauteils
DE102007057110B4 (de) 2007-11-26 2012-12-13 Eurocopter Deutschland Gmbh Verfahren zur Herstellung eines endlosen, dreidimensionalen geschlossenen Faserverbundwerkstoff-Halbzeugs
CN101462316A (zh) * 2007-12-19 2009-06-24 维斯塔斯风力系统有限公司 预成型件的制备方法
DE102008014657B4 (de) * 2008-03-17 2015-08-20 Airbus Defence and Space GmbH Verfahren zur Herstellung von Faserverbundbauteilen
DE102011006792B4 (de) * 2011-04-05 2017-07-27 Airbus Operations Gmbh Verfahren zum Herstellen und Verbinden von faserverstärkten Bauteilen sowie Luft- oder Raumfahrzeug
DE102011119224A1 (de) 2011-11-22 2012-05-10 Daimler Ag Herstellungsvorrichtung zu einer Herstellung eines Preforms eines Kraftfahrzeugbauteils
US9238338B2 (en) 2011-12-07 2016-01-19 The Boeing Company Method of fabricating composite laminate structures allowing ply slippage during forming
EP2802446B1 (fr) 2012-01-13 2020-11-18 Magna International Inc. Procede et systeme de fabrication d'un article composite
CN104924626B (zh) * 2015-06-23 2018-03-02 中国航空工业集团公司西安飞机设计研究所 一种复合材料纤维条、复合材料铺层及复合材料
DE102015223364B4 (de) * 2015-11-26 2017-11-16 Bayerische Motoren Werke Aktiengesellschaft Vorrichtung und Verfahren zum Herstellen von Textilverbundmaterialvorformlingen
CA2971066C (fr) * 2017-06-16 2024-05-28 Hutchinson Aeronautique & Industrie Ltee Procede de fabrication d'un panneau composite

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EP0465399A2 (fr) * 1990-05-29 1992-01-08 United Technologies Corporation Procédé pour fabriquer des articles conducteurs stratifiés
US5217766A (en) * 1990-09-06 1993-06-08 United Technologies Corporation Stabilized complex composite preforms

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EP2311618A3 (fr) * 2002-07-18 2013-08-14 Mitsubishi Rayon Co., Ltd. Préimprégné et méthode de fabrication d'un préimprégné
US8679991B2 (en) 2002-07-18 2014-03-25 Mitsubishi Rayon Co., Ltd. Prepreg, intermediate material for forming FRP, and method for production thereof and method for production of fiber-reinforced composite material
EP1900502A1 (fr) * 2006-09-13 2008-03-19 General Electric Company Procédé de fabrication d'un coin composite
EP2266784A1 (fr) 2009-06-22 2010-12-29 Eurocopter Deutschland GmbH Procédé pour la fabrication d'un composant de sandwich doté d'un cýur en nid d'abeille
EP2384884A1 (fr) * 2010-05-07 2011-11-09 Eurocopter Deutschland GmbH Procédé de fabrication d'une pièce composite renforcée et pièce composite renforcée obtenue selon ledit procédé
EP3034283A1 (fr) * 2014-12-18 2016-06-22 Airbus Operations Limited Procédé de fabrication d'une structure composite laminaire
EP3210768A3 (fr) * 2016-02-05 2017-11-22 Rohr, Inc. Procédé de fabrication de structures composites au moyen d'un film de résine combiné et d'un tissu sec
US11059206B2 (en) 2016-02-05 2021-07-13 Rohr, Inc Method for fabricating composite structures using combined resin film and dry fabric
EP3925767A3 (fr) * 2016-02-05 2022-03-30 Rohr, Inc. Procédé de fabrication de structures composites au moyen d'un film de résine combiné et d'un tissu sec
US11926078B2 (en) 2016-02-05 2024-03-12 Rohr, Inc Method for fabricating composite structures using combined resin film and dry fabric
CN109269855A (zh) * 2018-10-22 2019-01-25 西安航空制动科技有限公司 一种c纤维预制体力学性能试样的制备方法
CN109269855B (zh) * 2018-10-22 2020-11-17 西安航空制动科技有限公司 一种c纤维预制体力学性能试样的制备方法

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CA2358945A1 (fr) 2002-04-13
US20020053400A1 (en) 2002-05-09
EP1197315A3 (fr) 2004-01-28
DE10050851A1 (de) 2002-04-25
US20030138602A1 (en) 2003-07-24

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